CN207050700U - A kind of aircraft rudder surface angle displacement measuring device - Google Patents
A kind of aircraft rudder surface angle displacement measuring device Download PDFInfo
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- CN207050700U CN207050700U CN201720958091.9U CN201720958091U CN207050700U CN 207050700 U CN207050700 U CN 207050700U CN 201720958091 U CN201720958091 U CN 201720958091U CN 207050700 U CN207050700 U CN 207050700U
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- linear movement
- movement pick
- rudder face
- measuring device
- surface angle
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Abstract
The utility model discloses a kind of aircraft rudder surface angle displacement measuring device, belong to aeronautic measurement field of measuring technique.Described device includes the first linear movement pick-up (2) and the second linear movement pick-up (3), the telescopic end of first linear movement pick-up (2) and the second linear movement pick-up (3) is be hinged with rudder face (1), and the fixing end of the first linear movement pick-up (2) and the second linear movement pick-up (3) is hinged with hold-down support.The utility model is without complicated positioning and specialist tools, Fast Installation can be realized in narrow installing space, alignment error caused by avoiding more intermediate link simultaneously and sensor and measurement error caused by pivot center difference axle, accurate measurement can be realized to the angular displacement in larger rudder face stroke range.
Description
Technical field
The utility model belongs to aeronautic measurement field of measuring technique, and in particular to a kind of aircraft rudder surface angle displacement measurement dress
Put.
Background technology
At present in industrial design field, especially in the verification process of industrial design field, it is related to many angle displacement measurements
Problem is not easy to solve, such as aircraft control surface deflection angle.It is required that measurement moving component angular displacement in real time, for angular displacement sensor
Mounting means and measuring method requirement it is strict, for having multiple measurement points and operating mode is different everywhere, during the difference of space, design
And the cost that processed sensor fixture needs are paid is very high, and because the manufacturing and fixing error of fixture can cause measurement result not
Accurately.The requirement of various operating modes can be met without a kind of general device and measuring method at present.
A kind of angle displacement measuring device and measurement side are disclosed in Patent No. ZL201310195631.9 Chinese patent
Method, including angular displacement sensor, sensor support base, rocking arm, connecting rod, positioner.During measurement using locating piece and positioning foot rest,
Positioning beam is as positioner, to position cornual plate on angular displacement sensor and measured piece on the basis of the effective length of rocking arm and connecting rod
Position, and angular displacement sensor, rocking arm, connecting rod, small bearing are sequentially connected, the angular displacement of measured piece are converted into rocking arm
Angular displacement, so as to which the angular displacement to measured piece measures.The measurement apparatus and measuring method can effectively measure ground experiment
In rudder face angular displacement, it is but difficult to the rudder face angular displacement during flight control system experiment and practical flight because space limits
With measurement, and implementation steps and intermediate link are more, and connecting rod, the installation gap of rocking arm and error can influence measurement result
Accuracy.
Utility model content
In order to solve the above problems, the utility model proposes a kind of aircraft rudder surface angle displacement measuring device, and bag can be achieved
Include the measurement of a variety of environment such as ground experiment, flight control system experiment and practical flight process and operating mode lower rudder face angle displacement, structure
Simply, easy for installation, measurement range is big, precision is high, and functional reliability is high.
The utility model aircraft rudder surface angle displacement measuring device, including the first linear movement pick-up and the second displacement of the lines sensing
The telescopic end of device, the first linear movement pick-up and the second linear movement pick-up is hinged with rudder face, the first linear movement pick-up and
The fixing end of second linear movement pick-up is hinged with hold-down support.
Preferably, the first linear movement pick-up and the second linear movement pick-up are dragline type linear movement pick-up.
Preferably, the first linear movement pick-up and the second linear movement pick-up are that the redundance containing multigroup coil is stretched
Contracting rod-type linear movement pick-up.
Preferably, 2 points that are articulated with rudder face of first linear movement pick-up and the second linear movement pick-up on
The neutral surface of rudder face is symmetrical.
Preferably, be articulated with hold-down support the two of first linear movement pick-up and the second linear movement pick-up
Point is symmetrical on the neutral surface of rudder face.
Preferably, 2 points that are articulated with rudder face of first linear movement pick-up and the second linear movement pick-up are formed
Minor arc at 150 °~170 °.
Rudder face angular displacement and the first linear movement pick-up and the second linear movement pick-up have respectively corresponding relation F (x1) and
F (x2), and F (x1) and F (x2) obeys the cosine law.
The value of rudder face angular displacement can take two linear movement pick-ups after corresponding relation F (x1) and F (x2) is solved
Weighted average, wherein sensor body axis and rudder face center of rotation-sensor telescopic end and rudder face pin joint can also be taken
The value of angular displacement that line obtains closer to the linear movement pick-up of 90 degree of that sides by solution.
The utility model is positioned without complexity and specialist tools, can realize Fast Installation in narrow installing space,
Alignment error caused by avoiding more intermediate link simultaneously and sensor and measurement error caused by pivot center difference axle, energy
Accurate measurement is realized in enough angular displacements in larger rudder face stroke range.
Brief description of the drawings
Fig. 1 is the structural representation according to a preferred embodiment of the utility model aircraft rudder surface angle displacement measuring device.
Fig. 2 is structural representation under the angular displacement deflection situation of embodiment illustrated in fig. 1.
Wherein, 1 is rudder face, and 2 be the first linear movement pick-up, and 3 be the second linear movement pick-up, and 101 be the rudder face neutral conductor,
102 be rudder face horizontal line, and 103 be deflection wire, and 201 be the first telescopic end pin joint, and 202 be the first fixing end pin joint, and 301 are
Second telescopic end pin joint, 302 be the second fixing end pin joint.
Embodiment
To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the embodiment of the utility model is further described in more detail.In the accompanying drawings, from beginning
Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Described reality
It is the utility model part of the embodiment to apply example, rather than whole embodiments.Below with reference to the embodiment of accompanying drawing description
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belong to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of description the utility model and simplifies description, rather than indicates or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
The utility model proposes a kind of aircraft rudder surface angle displacement measuring device, as shown in figure 1, being passed including the first displacement of the lines
The telescopic end of the linear movement pick-up 3 of sensor 2 and second, the first linear movement pick-up 2 and the second linear movement pick-up 3 is and rudder face
1 is be hinged, and the fixing end of the first linear movement pick-up 2 and the second linear movement pick-up 3 is hinged with hold-down support.
Specifically, the telescopic end of the first linear movement pick-up 2 and rudder face are articulated with the first telescopic end pin joint 201, first
The fixing end of linear movement pick-up 2 is articulated with the first fixing end pin joint 202 with hold-down support；Second linear movement pick-up 3
Telescopic end is articulated with the second telescopic end pin joint 301 with rudder face, and the fixing end of the second linear movement pick-up 3 is hinged with hold-down support
In the second fixing end pin joint 302.
With reference to figure 2, after rudder face deflects α angles to the left, left side the first telescopic end pin joint 201 is to close to hold-down support
Direction is moved, i.e., is recovered to the telescopic end of the first linear movement pick-up 2 in the cylinder where its fixing end, conversely, right side the
Two telescopic end pin joints 301 move to the direction away from hold-down support, i.e., consolidate the telescopic end of the second linear movement pick-up 3 from it
Pulled out in cylinder where fixed end.
In the present embodiment, the shown rudder face center of circle is O, radius R, it is to be understood that as shown in Fig. 2 control surface deflection angle
Spend the displacement x existence function relation of β and the second linear movement pick-up 3, the functional relation is smaller and the second telescopic end is cut with scissors in β angles
Contact 301 closer to rudder face horizontal line when, can be represented with cosine function, i.e. x=Rcos β.
Therefore, in the present embodiment, the linear movement pick-up 3 of the first linear movement pick-up 2 and second is articulated with rudder face
2 points of formation minor arcs at 150 °~170 °, with reference to figure 1 or Fig. 2, make the first telescopic end pin joint 201 and second flexible as far as possible
End pin joint 301 refers to perpendicular to the straight of the rudder face neutral conductor 101 close to rudder face horizontal line 102, rudder face horizontal line described here
Footpath.On the other hand, when control surface deflection angle beta is more than set angle α, it is preferred to use the range of one of linear movement pick-up
As measured value, the reference point of the solution value of a not outer linear movement pick-up as rudder face angular displacement, for example, in the present embodiment
α is chosen for 15 °, with reference to figure 2, now, control surface deflection angle is carried out on the basis of the measured value of second linear movement pick-up on right side
Degree solves, and selection principle is sensor body axis and rudder face center of rotation-sensor telescopic end and rudder face pin joint line
The linear movement pick-up of (hereinafter referred to as deflection wire 103) closer 90 degree of that sides, such as the biography of the linear movement pick-up of right side second
Sensor body axis is with deflection wire 103 closer to 90 °.
It is understood that being in rudder face angular displacement in the range of α, the value of rudder face angular displacement takes two linear movement pick-ups
Weighted average after corresponding relation F (x1) and F (x2) is solved.Broken down when there is one in two linear movement pick-ups
Afterwards, the value of aircraft rudder surface angular displacement is value of the linear movement pick-up of non-faulting side after solution.
In the present embodiment, the first linear movement pick-up 2 and the second linear movement pick-up 3 are dragline type displacement of the lines sensing
Device, or be the redundance Telescopic shaft type linear movement pick-up containing multigroup coil.
In the present embodiment, 2 points that are articulated with rudder face of the linear movement pick-up 3 of the first linear movement pick-up 2 and second
Neutral surface on rudder face is symmetrical.Similarly, being articulated with for the linear movement pick-up 3 of the first linear movement pick-up 2 and second is consolidated
The 2 points of neutral surfaces on rudder face determined on bearing are symmetrical, with reference to figure 1 or Fig. 2.
The utility model provides a kind of aircraft rudder surface angle displacement measuring device, can be achieved to include ground experiment, flies control system
A variety of environment such as system experiment and practical flight process and the measurement of operating mode lower rudder face angle displacement, using redundance linear movement pick-up
As survey tool, the measurement of angular displacement is converted into the measurement of displacement of the lines using simple mathematical relationship, measurement range is big, essence
Degree is high, and reliability is high, simple in construction, easy for installation, can be in narrow installing space without complexity positioning and specialist tools
Fast Installation is realized, while alignment error caused by avoiding more intermediate link and sensor cause with pivot center difference spindle guide
Measurement error, accurate measurement can be realized to the angular displacement in larger rudder face stroke range.
It is last it is to be noted that：Above example is only to illustrate the technical solution of the utility model, rather than it is limited
System.Although the utility model is described in detail with reference to the foregoing embodiments, one of ordinary skill in the art should manage
Solution：It can still be modified to the technical scheme described in foregoing embodiments, or which part technical characteristic is entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the utility model
The spirit and scope of technical scheme.
Claims (6)
1. a kind of aircraft rudder surface angle displacement measuring device, it is characterised in that including the first linear movement pick-up (2) and the second line position
The telescopic end of displacement sensor (3), the first linear movement pick-up (2) and the second linear movement pick-up (3) is be hinged with rudder face (1),
The fixing end of first linear movement pick-up (2) and the second linear movement pick-up (3) is hinged with hold-down support.
2. aircraft rudder surface angle displacement measuring device as claimed in claim 1, it is characterised in that the first linear movement pick-up (2)
It is dragline type linear movement pick-up with the second linear movement pick-up (3).
3. aircraft rudder surface angle displacement measuring device as claimed in claim 1, it is characterised in that the first linear movement pick-up (2)
It is the redundance Telescopic shaft type linear movement pick-up containing multigroup coil with the second linear movement pick-up (3).
4. aircraft rudder surface angle displacement measuring device as claimed in claim 2 or claim 3, it is characterised in that first displacement of the lines passes
2 points of neutral surfaces on rudder face for being articulated with rudder face of sensor (2) and the second linear movement pick-up (3) are symmetrical.
5. aircraft rudder surface angle displacement measuring device as claimed in claim 2 or claim 3, it is characterised in that first displacement of the lines passes
Be articulated with hold-down support two points of neutral surfaces on rudder face of sensor (2) and the second linear movement pick-up (3) are symmetrical.
6. aircraft rudder surface angle displacement measuring device as claimed in claim 1, it is characterised in that first linear movement pick-up
(2) and the second linear movement pick-up (3) be articulated with rudder face 2 points formation minor arcs at 150 °~170 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720958091.9U CN207050700U (en) | 2017-08-02 | 2017-08-02 | A kind of aircraft rudder surface angle displacement measuring device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720958091.9U CN207050700U (en) | 2017-08-02 | 2017-08-02 | A kind of aircraft rudder surface angle displacement measuring device |
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| CN207050700U true CN207050700U (en) | 2018-02-27 |
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| CN201720958091.9U Active CN207050700U (en) | 2017-08-02 | 2017-08-02 | A kind of aircraft rudder surface angle displacement measuring device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108454882A (en) * | 2018-04-08 | 2018-08-28 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of driving of rudder face and rudder face angle measuring mechanism |
-
2017
- 2017-08-02 CN CN201720958091.9U patent/CN207050700U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108454882A (en) * | 2018-04-08 | 2018-08-28 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of driving of rudder face and rudder face angle measuring mechanism |
| CN108454882B (en) * | 2018-04-08 | 2023-11-28 | 中国空气动力研究与发展中心计算空气动力研究所 | Control surface driving and control surface angle measuring mechanism |
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